Accession Number : ADA301567
Title : Graphite/Epoxy Composite Stiffened Panel Fabrication Development.
Descriptive Note : Contract rept.,
Corporate Author : MCDONNELL DOUGLAS CORP LONG BEACH CA DOUGLAS AIRCRAFT DIV
Personal Author(s) : Palmer, R. J.
PDF Url : ADA301567
Report Date : MAR 1984
Pagination or Media Count : 136
Abstract : A stiffened composite panel design technology program was initiated in 1974 with the objective of providing a test-verified, stiffened-panel, minimum-mass data base. Stress resultant levels in the program varied between inch and 25,OOO lbs./inch. Panel sizes varied from 6 by 18 inches with a single stiffener to 30 by 60 inches and six stiffeners. All panels were manufactured with stiffeners integrally molded in place. Designs were optimized for load versus mass by variations in fiber pattern and "hat, "J," "I," sine wave "I," solid bade and honeycomb blade stiffener shapes and sizes. The scope of this report is to present the manufacturing development experiences for each type of stiffened panel design. Details of tooling, bag materials, methods of layup and problems associated with fabrication are documented. Both successful and unsuccessful manufacturing techniques are described. Recommendations for the best state-of-the-art manufacturing techniques are detailed for each general configuration.
Descriptors : *AIRCRAFT, *STIFFNESS, *STIFFENING, *RUBBER, *ALUMINUM, *FUSELAGES, *WINGS, *GRAPHITE EPOXY COMPOSITES, *MANDRELS, COMPRESSION, THICKNESS, FIBERS, MANUFACTURING, STRESS ANALYSIS, TOOLS, LAMINATES, LOADS(FORCES), PANELS, DEFORMATION, FIBER REINFORCED COMPOSITES, FABRICATION, STRENGTH(MECHANICS), SHEAR STRESSES, BUCKLING, WALLS, DESIGN CRITERIA, AXIAL LOADS, SILICONES, SINE WAVES, FOAM, HONEYCOMB STRUCTURES, TETRAFLUOROETHYLENE RESINS.
Subject Categories : Aircraft
Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE